- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
- As part of a NASA funded contract to develop and demonstrate a gas generator cycle hybrid rocket motor for upper stage space motor applications, the development and demonstration of a low sensitivity, high performance fuel composition was undertaken. The ultimate goal of the development program was to demonstrate successful hybrid operation (start, stop, throttling) of the fuel with high concentration (90+%) hydrogen peroxide. The formulation development and lab-scale testing of a simple DOT Class 1.4c gas generator propellant is described. Both forward injected center perforated and aft injected end burner hybrid combustion behavior were evaluated with gaseous oxygen and catalytically decomposed 90% hydrogen peroxide. Cross flow and static environments were found to yield profoundly different combustion behaviors, which were further governed by binder type, oxidizer level and, significantly, oxidizer particle size. Primary extinguishment was accomplished via manipulation of PDL behavior and oxidizer turndown, which is enhanced with the hydrogen peroxide system. Laboratory scale combustor results compared very well with 11-inch and 24-inch sub-scale test results with 90% hydrogen peroxide.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 20020023460.
AIAA Paper 2001-3244.
37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; 8-11 Jul. 2001; Salt Lake City, UT; United States.
- Copyright, Distribution as joint owner in the copyright.
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